Compressor turbine vane airfoil profile

a compressor turbine and airfoil technology, which is applied in the direction of propellers, propulsive elements, water-acting propulsive elements, etc., can solve the problems of harshness to the total thrust or power capability of the engine, compressor or hp turbine, etc., and achieve the effect of reducing shock losses and minimizing secondary losses

Active Publication Date: 2011-01-04
PRATT & WHITNEY CANADA CORP
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Benefits of technology

[0004]The present invention equalizes the static pressure gradient in the spanwise direction, to minimize secondary losses and to beneficially align the flow entering the HT blade stage. The design also provides an optimized tip section to reduce shock losses.

Problems solved by technology

Over and above this, the airfoil is subject to flow regimes which lend themselves easily to flow separation, which tend to limit the amount of work transferred to the compressor, and hence the total thrust or power capability of the engine.
The compressor or HP turbine is also subject to harsh temperatures and pressures, which require a solid balance between aerodynamic and structural optimization.

Method used

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  • Compressor turbine vane airfoil profile
  • Compressor turbine vane airfoil profile
  • Compressor turbine vane airfoil profile

Examples

Experimental program
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Embodiment Construction

[0015]FIG. 1 illustrates a turboshaft engine 10 of a type preferably provided for use in subsonic flight, generally comprising in serial flow communication a centrifugal compressor 14 for pressurizing the air, a combustor 16 in which the compressed air is mixed with fuel and ignited for generating an annular stream of hot combustion gases, and a turbine section 18 for extracting energy from the combustion gases to drive the compressor 14 and an output shaft 12.

[0016]The turbine section 18 comprises a single stage compressor turbine 20 and a power turbine 22. The compressor turbine 20 drives the compressor 14, whereas the power turbine drives the output shaft 12.

[0017]FIG. 2 illustrates a portion of an annular hot gaspath, indicated by arrows 27 and defined by annular inner and outer walls 28 and 30 respectively, for directing the stream of hot combustion gases axially in an annular flow. The profile of the inner and outer walls 28 and 30 of the annular gaspath, “cold” (i.e. non-oper...

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Abstract

A single stage high pressure turbine vane includes an airfoil having a profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoothly connected by an appropriate continuing curve, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape.

Description

TECHNICAL FIELD[0001]The invention relates generally to a vane airfoil for a gas turbine engine and, more particularly, to an airfoil profile suited for a high pressure turbine (HPT) stage vane.BACKGROUND OF THE ART[0002]Where a vane airfoil is part of a single stage turbine driving a compressor (i.e. part of a high pressure or HP turbine), the requirements for such a vane airfoil design are significantly more stringent than multiple stage airfoil designs, as the compressor relies solely on this single stage HP turbine to deliver all the required work, as opposed to work being spread over several turbine stages. Over and above this, the airfoil is subject to flow regimes which lend themselves easily to flow separation, which tend to limit the amount of work transferred to the compressor, and hence the total thrust or power capability of the engine. The compressor or HP turbine is also subject to harsh temperatures and pressures, which require a solid balance between aerodynamic and ...

Claims

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Application Information

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Patent Type & Authority Patents(United States)
IPC IPC(8): B64C27/46
CPCF01D5/141F05D2250/74F05D2240/301Y10S416/02
Inventor SLEIMAN, MOHAMADDION, MICHELGIRGIS, SAMI
Owner PRATT & WHITNEY CANADA CORP
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